Seal system
A seal arrangement for a turbo-engine, for sealing a peripheral gap between a rotor and a stator is provided. The stator a seal holder provided with at least one groove for respectively receiving a segmented, dynamic seal. Segments of the dynamic seal are made up of a plurality of brush seal segments, and free ends of bristles of the brush seal segments extend in the radial direction project from the respective groove and lie on the rotor. The or every groove for receiving the brush-type seal segments is designed without an undercut, the brush-type seal segments being received in the respective groove without an undercut in a positive manner.
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The present invention relates to a seal system for a turbo-engine for sealing a circumferential gap between a rotor and a stator and to a seal system for a turbo-engine for sealing a gap between two stator-side components. Furthermore, the present invention relates to a turbo-engine, a gas turbine, and a steam turbine.
BACKGROUNDGas turbines are composed of multiple subassemblies such as at least one compressor, one combustion chamber, and at least one turbine. The or each compressor and the or each turbine have a rotor which rotates with respect to a stationary stator. The stator is, in particular, a stationary housing having associated stationary guide vanes. The rotor has associated rotor blades which rotate with the rotor with respect to the stationary guide vanes and the stationary housing.
To optimize the efficiency of gas turbines, leakage flows must be minimized. This applies, on the one hand, to leakage flows between components rotating relative to each other and, on the other hand, to leakage flows between stationary components. Seal systems for sealing a gap between components rotating relative to each other are referred to as dynamic seal systems. Seal systems for sealing a gap between stationary components are referred to as static seal systems.
Brush seals have been found satisfactory for sealing gaps between components rotating relative to each other or between stationary components. Brush seals have a plurality of wire-type bristles attached to a bristle holder. A groove is integrated into one of the components defining the gap to be sealed; the bristle holder is positioned in the groove from which free ends of the bristles project outward, these free ends of the bristles contacting another component defining the gap. To secure the brush seal in a groove, the groove has a so-called undercut, which constricts sections of the groove and positively secures the bristle holder of the brush seal in the groove. The manufacture of undercut grooves is technically complex and expensive and therefore disadvantageous overall.
SUMMARY OF THE INVENTIONOn this basis, the object of the present invention is to provide a novel seal system.
The present invention provides a seal system for a turbo-engine for sealing a circumferential gap between a rotor and a stator, the stator having a seal holder having at least one circumferential groove for receiving a segmented dynamic seal, segments of the dynamic seal being designed as brush seal elements, and the free ends of the bristles of the brush seal segments extending in the radial direction projecting from the particular groove and resting on the rotor. According to the present invention, the or each groove for receiving brush seal segments is designed as a groove without undercut, the brush seal segments being positively secured in the particular groove without an undercut, preferably by at least one clamping element each.
According to the present invention, it is proposed that the groove for receiving the brush seal segments be designed without undercut. This reduces the manufacturing complexity for the grooves, so that the seal systems made of brush seals may be manufactured more cost-effectively overall.
According to an advantageous refinement of the present invention, the brush seal segments are caulked in the particular groove without undercut; for this purpose, a lip-shaped clamping element of the particular groove is bent in the direction of the brush seal segment to be caulked to constrict the particular groove and to positively secure the brush seal segment in the particular groove.
According to an advantageous refinement of the present invention, the brush seal segments are secured in the particular groove without undercut by pin-type or screw-type clamping elements passing through bore holes; at least one clamping element is positioned in the area of each brush seal segment, and the particular clamping element constricts the particular groove and positively secures the brush seal segment in the particular groove.
The present invention also provides a seal system for a turbo-engine for sealing a gap between two stator-side components, a first stator-side component having a seal holder having at least one groove for receiving a static seal, the static seal being designed as a brush seal, and the free ends of the bristles of the brush seal projecting from the particular groove and resting on the second stator-side component. According to the present invention, the or each groove for receiving the brush seal is designed as a groove without undercut, the brush seal being secured in the particular groove without undercut with a radial clearance.
Exemplary embodiments of the present invention are explained in greater detail on the basis of the drawing without being limited thereto.
The present invention is described below in greater detail with reference to
In the exemplary embodiment shown in
According to the present invention, it is proposed that groove 15 for receiving brush seal segments 16 be designed without undercut. A receptacle section 23 of groove 15 without undercut therefore has the same axial width over the entire radial height. In this groove 15 without undercut, i.e., receptacle section 23 thereof without undercut, brush seal segment 16 is positively secured in the area of bristle holder 18, specifically with the aid of a clamping element.
In the exemplary embodiment of
In the exemplary embodiment of
In the exemplary embodiment of
Of course, similarly to the embodiment of
To assemble seal systems 39 and 40 of the exemplary embodiments according to
All seal systems of
As mentioned previously, the brush seals are composed of brush seal segments, each brush seal segment extending over a defined angular section of the circumference of the groove. It should be mentioned that, of course, seal holder 14 may also be segmented. Seal holder 14 may thus be composed of a plurality of seal holder segments, each seal holder segment extending over a defined circumferential section; one or more brush seal segments may be positioned in each seal holder segment. The seal holder segments together form the seal holder.
In the exemplary embodiment of
The seal systems according to the present invention are preferably used in turbo-engines, in particular in gas turbines such as in aircraft engines. The dynamic seal systems according to
Claims
1. A seal system for a turbo-engine, for sealing a circumferential gap between a rotor and a stator, the stator comprising a seal holder having at least one circumferential groove for receiving a segmented dynamic seal, the segmented dynamic seal including a plurality of segments; each of the segments being brush seal segments having bristles, the bristles having free ends, the free ends of the bristles extending in a radial direction projecting from the at least one groove and resting on the rotor, the at least one groove being a groove without undercut, the brush seal segments being positively secured in the groove;
- wherein the at least one groove includes a plurality of axially spaced circumferential grooves, each receiving a respective one of a plurality of brush seal segments, two adjacent grooves of the plurality of grooves being connected by at least one bore hole extending in an axial direction, the brush seal segments being positively secured in the grooves by clamping elements passing through the bore holes.
2. The seal system as recited in claim 1,
- wherein the groove has a uniform axial width, in at least one receptacle section for the brush seal segments, over its entire radial height.
3. The seal system as recited in claim 1,
- wherein the bristles of one of the brush seal segments rest axially on a radially longer side wall of the groove, the side wall of the groove forming a support element.
4. The seal system as recited in claim 1,
- wherein the clamping elements are pin-type or screw-type clamping elements.
5. The seal system as recited in claim 4,
- wherein the or each clamping element is designed as a passing pin or a headless screw.
6. The seal system as recited in claim 1,
- wherein the seal holder is segmented such that a plurality of seal holder segments extends over the circumference of the rotor, and together forms a circular ring-shaped seal holder.
7. A seal system for a turbo-engine for sealing a gap between two stator-side components comprising a first stator-side component and a second stator-side component, the first stator-side component having at least one groove for receiving a static seal, the static seal being designed as a brush seal having bristles, the bristles having free ends, the free ends of the bristles projecting from the groove and resting on a second stator-side component,
- the groove being a groove without undercut, the brush seal being secured in the groove with a radial clearance; wherein the at least one groove includes a plurality of axially spaced circumferential grooves, each receiving a respective one of a plurality of brush seal segments, two adjacent grooves of the plurality of grooves being connected by at least one bore hole extending in an axial direction, the brush seal segments being positively secured in the grooves by clamping elements passing through the bore holes.
8. The seal system as recited in claim 7,
- wherein in a receptacle section for the brush seal, the groove has a uniform radial height over its entire axial width.
9. A turbo-engine having at least one seal system as recited in claim 1.
10. A gas turbine, an aircraft engine in particular, having at least one seal system as recited in claim 1.
11. A steam turbine having at least one seal system as recited in claim 1.
12. A turbo-engine having at least one seal system as recited in claim 7.
13. A gas turbine, an aircraft engine in particular, having at least one seal system as recited in claim 7.
14. A steam turbine having at least one seal system as recited in claim 7.
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- International Preliminary Examination Report RCT/DE2006/000210 (6 pages).
Type: Grant
Filed: Feb 8, 2006
Date of Patent: Nov 16, 2010
Patent Publication Number: 20080258403
Assignee: MTU Aero Engines GmbH (Munich)
Inventors: Stefan Beichl (Herrsching), Alfons Gail (Friedberg)
Primary Examiner: Shane Bomar
Assistant Examiner: Kipp C Wallace
Attorney: Davidson, Davidson & Kappel, LLC
Application Number: 11/884,643
International Classification: F01D 11/02 (20060101);